A jet injection unit structure and a bi-component injector

Abstract

The present invention relates to the technical field of jet burners, and particularly relates to a jet unit structure and a dual-component injector. The jet unit structure includes: a fuel nozzle having at least one radial hole provided on its side wall; an oxidizer nozzle, at least a part of which is sleeved inside the fuel nozzle; the interior of the oxidizer nozzle is penetrated and is in communication with the radial hole and a jet port together. In the jet unit structure provided by the present invention, the fuel nozzle and the oxidizer nozzle are arranged in a nested structure, so that the first end of the oxidizer nozzle and the radial hole provided on the side wall of the fuel nozzle jointly form a jet port with the second end of the fuel nozzle.

Description

Technical Field

[0001] The present invention relates to the technical field of injection burners, and particularly to an injection unit structure and a bi-propellant injector. Background Art

[0002] The injector is a core component of a liquid rocket engine. It is located at the head of the thrust chamber. Its function is to evenly inject the propellants into the combustion chamber under the specified propellant flow rate, mixture ratio, and injection pressure drop, ensuring that the mixture ratio and mass distribution meet the design state requirements, and quickly completing the atomization and mixing processes of the propellants, so that the propellants burn efficiently and fully in the combustion chamber. The design level and processing accuracy of the injector have a great impact on the stability, efficiency, and life of the combustion chamber. For every one percentage point loss in the combustion efficiency organized by the injector, it means the same percentage loss in the specific impulse performance of the engine. Generally, the combustion efficiency of the thrust chamber of a large-thrust liquid rocket engine is above 96%, and the combustion chamber efficiency of an excellent injector can reach 99%. As an important part of the injector, the structure form of the injection unit structure also has a great impact on the combustion stability of the injector. In the prior art, the structure form of the injection unit structure is often relatively single, with poor anti-interference ability and low stability, and there is still much room for improvement. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defect of low stability of the injection unit structure in the prior art, so as to provide an injection unit structure with higher stability.

[0004] Another technical problem to be solved by the present invention is to overcome the defect of low combustion efficiency of the bi-propellant injector in the prior art, so as to provide a bi-propellant injector with higher combustion efficiency.

[0005] To solve the above technical problems, an injection unit structure provided by the present invention includes:

[0006] A fuel nozzle, on the side wall of which there is provided at least one radial hole;

[0007] An oxidizer nozzle, at least part of which is sleeved inside the fuel nozzle;

[0008] The inside of the oxidizer nozzle is penetrated and is in communication with the radial hole and the injection port together.

[0009] Further, at least one throttling hole is provided on the inner side wall of the end of the oxidizer nozzle away from the injection port.

[0010] Further, two throttling holes are continuously provided on the inner side wall of the end of the oxidizer nozzle away from the injection port.

[0011] Further, the radial holes are in a raindrop shape structure.

[0012] Further, an annular cavity is formed between the inner side wall of the fuel agent nozzle and the outer side wall of the oxidant nozzle.

[0013] Further, the radial holes are arranged facing the annular cavity.

[0014] Further, an annular gap is also formed between the inner side wall of the fuel agent nozzle and the outer side wall of the oxidant nozzle. One end of the annular gap communicates with the annular cavity, and the other end communicates with the injection port.

[0015] The dual-component injector provided by the present invention includes:

[0016] A fuel agent cavity;

[0017] A first bottom surface, arranged at the bottom of the fuel agent cavity;

[0018] A second bottom surface, arranged at the top of the fuel agent cavity and opposite to the first bottom surface; and

[0019] At least one injection unit structure as described above, and the injection unit structures are connected and arranged between the first bottom surface and the second bottom surface.

[0020] Further, both the first bottom surface and the second bottom surface are curved surface structures, and the curved middle parts are close to each other, so that the fuel agent cavity is constructed into a hyperbolic concave lens type structure.

[0021] Further, a plurality of injection unit structures with different lengths are arranged between the first bottom surface and the second bottom surface.

[0022] The technical solution of the present invention has the following advantages:

[0023] 1. In the injection unit structure provided by the present invention, the fuel agent nozzle and the oxidant nozzle are arranged in a nested structure, so that the first end of the oxidant nozzle and the radial holes arranged on the side wall of the fuel agent nozzle jointly communicate with the injection port formed by the second end of the fuel agent nozzle.

[0024] 2. In the injection unit structure provided by the present invention, the throttle hole protrudes from the inner wall of the oxidant nozzle towards the central position, so that the flow area at the throttle hole is reduced. The oxidant nozzle adopts a double throttle hole design, which can enhance the anti-interference ability of the oxidant during flow, thereby enhancing the combustion stability of the injector.

[0025] 3. In the injection unit structure provided by the present invention, the radial holes with a raindrop shape structure are adopted, which can improve the flow coefficient of the fuel agent nozzle and is beneficial to reducing the flow resistance of the fuel agent nozzle at the same injection speed.

[0026] 4. In the injection unit structure provided by the present invention, the annular cavity can enhance the stability and uniformity of the fuel flow in the annular gap.

[0027] 5. In the injection unit structure provided by the present invention, the radial hole is arranged opposite to the annular cavity, so that after the fuel enters the injection unit structure through the radial hole, it preferentially enters the annular cavity, which is equivalent to a collector and plays a role in flow equalization.

[0028] 6. In the bicomponent injector provided by the present invention, both the first bottom surface and the second bottom surface are curved surface structures, thereby improving the pressure-bearing capacity of the fuel chamber. Since the pressure-bearing capacity of a curved surface is higher than that of a flat surface with the same thickness, the curved surface can evenly disperse the pressure along the entire surface and evenly diffuse the pressure to all parts of the bottom surface, so that the curved surface can withstand greater pressure, thereby improving the structural strength of the bicomponent injector.

[0029] 7. In the two-component injector provided by the present invention, the fuel chamber is constructed as a hyperbolic concave lens structure, and the curved middle parts of the first bottom surface and the second bottom surface are close to each other, so that the fuel flow rate in the edge area of the fuel chamber is lower, and the fuel flow rate in the central area of the fuel chamber is higher, thereby making the fuel chamber have an isostatic uniform flow characteristic, and the flow distribution of each injection unit structure is more uniform, which is beneficial to improving the injection combustion efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0031] Figure 1 The cross-sectional view of the bicomponent injector of the present invention is shown in FIG. Figure 1 ;

[0032] Figure 2 for Figure 1 Enlarged view of point A in the middle;

[0033] Figure 3 It is a schematic diagram of the structure of the injection unit of the present invention;

[0034] Figure 4 The cross-sectional view of the bicomponent injector of the present invention is shown in FIG. Figure 2 ;

[0035] Figure 5 It is a schematic diagram of the first bottom cross-section of the present invention.

[0036] Description of reference numerals:

[0037] 10 - First bottom surface, 11 - transpiration cooling channels, 20 - second bottom surface, 30 - third bottom surface;

[0038] 40 - Oxidizer chamber, 41 - oxidizer inlet, 50 - fuel agent chamber, 51 - fuel agent inlet;

[0039] 60 - Oxidizer nozzle, 61 - oxidizer nozzle inlet end, 62 - throttle orifice, 63 - oxidizer nozzle outlet end;

[0040] 70 - Fuel agent nozzle, 71 - radial holes, 72 - annular cavity, 73 - annular gap, 74 - injection orifice;

[0041] 80 - Combustion chamber. Detailed implementation manners

[0042] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0043] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0044] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0045] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0046] Embodiment 1

[0047] Combined with Figures 1-3As shown, this embodiment provides a jet unit structure, including:

[0048] A fuel nozzle 70, on the side wall of which there is at least one radial hole 71;

[0049] An oxidant nozzle 60, at least part of which is sleeved inside the fuel nozzle 70;

[0050] The inside of the oxidant nozzle 60 is penetrated and is communicated with the jet port 74 together with the radial hole 71.

[0051] Preferably, at least part of the oxidant nozzle 60 is sleeved inside the fuel nozzle 70. The first end of the fuel nozzle 70 is connected to the outer wall of the oxidant nozzle 60, and the second end of the fuel nozzle 70 is configured as a jet port 74; the inside of the oxidant nozzle 60 is penetrated. The end of the oxidant nozzle 60 away from the jet port 74 is configured as an oxidant nozzle inlet end 61, and the end of the oxidant nozzle 60 close to the jet port 74 is configured as an oxidant nozzle outlet end 63, so that the oxidant nozzle inlet end 61 is communicated with the jet port 74 via the oxidant nozzle outlet end 63; at the same time, at least one radial hole 71 provided on the side wall of the fuel nozzle 70 is also communicated with the jet port 74.

[0052] The oxidant nozzle inlet end 61 is adapted to introduce oxidant, and at least one radial hole 71 provided on the side wall of the fuel nozzle 70 is adapted to introduce fuel. After passing through the jet unit structure, the oxidant and the fuel are mixed and discharged together from the jet port 74.

[0053] For the jet unit structure provided in this embodiment, the fuel nozzle 70 and the oxidant nozzle 60 are arranged in a nested structure, so that the first end of the oxidant nozzle 60 and the radial hole 71 provided on the side wall of the fuel nozzle 70 are jointly communicated with the jet port 74 formed by the second end of the fuel nozzle 70.

[0054] Preferably, each fuel nozzle 70 is provided with 2 rows of radial holes 71, 4 in each row, and the radial holes 71 are evenly distributed circumferentially on the side wall of the fuel nozzle 70.

[0055] Specifically, at least one throttle hole 62 is provided on the inner sidewall of the end of the oxidizer nozzle 60 away from the injection port 74, that is, at least one throttle hole 62 is provided at the inlet end 61 of the oxidizer nozzle. As a further preferred form, two throttle holes 62 are continuously provided on the inner sidewall of the end of the oxidizer nozzle 60 away from the injection port 74. The throttle hole 62 protrudes from the inner wall of the oxidizer nozzle 60 towards the central position, so that the flow area at the throttle hole 62 is reduced. The oxidizer nozzle 60 adopts a double throttle hole design, which can enhance the anti-interference ability of the oxidizer during flow, thereby enhancing the combustion stability of the injector.

[0056] Specifically, the radial hole 71 has a raindrop-shaped structure. Using a radial hole with a raindrop-shaped structure can improve the flow coefficient of the fuel agent nozzle 70, and is beneficial to reducing the flow resistance of the fuel agent nozzle 70 at the same injection speed.

[0057] Specifically, an annular cavity 72 is formed between the inner sidewall of the fuel agent nozzle 70 and the outer sidewall of the oxidizer nozzle 60.

[0058] Specifically, an annular gap 73 is further formed between the inner sidewall of the fuel agent nozzle 70 and the outer sidewall of the oxidizer nozzle 60. One end of the annular gap 73 is communicated with the annular cavity 72, and the other end is communicated with the injection port 74.

[0059] The annular cavity 72 can enhance the stability and uniformity of the fuel agent flow at the annular gap 73.

[0060] Specifically, the radial hole 71 is arranged facing the annular cavity 72, so that after the fuel agent enters the injection unit structure from the radial hole 71, it preferentially enters the annular cavity 72, acting as a collector and playing a role in equalizing the flow.

[0061] Embodiment 2

[0062] Combined with Figure 1 As shown, this embodiment provides a dual-component injector, including:

[0063] Fuel agent chamber 50;

[0064] The first bottom surface 10 is arranged at the bottom of the fuel agent chamber 50;

[0065] The second bottom surface 20 is arranged at the top of the fuel agent chamber 50 and is oppositely arranged with the first bottom surface 10; and

[0066] At least one injection unit structure as described above, and the injection unit structure is communicatively arranged between the first bottom surface 10 and the second bottom surface 20.

[0067] Specifically, the first bottom surface 10 and the second bottom surface 20 are both curved structures, and the curved middle parts are close to each other, so that the fuel chamber 50 is constructed as a hyperbolic concave lens structure.

[0068] Preferably, the fuel chamber 50 is constructed as a closed or partially open cavity structure, the bottom and top of which are respectively enclosed by a first bottom surface 10 and a second bottom surface 20, and at least one injection unit structure is arranged between the first bottom surface 10 and the second bottom surface 20, that is, the injection unit structure is arranged in the fuel chamber 50, and the injection unit structure is opened up and down, penetrating the first bottom surface 10 and the second bottom surface 20, thereby connecting the upper space of the second bottom surface 20 with the lower space of the first bottom surface 10.

[0069] The present embodiment provides a bipropellant injector, wherein the first bottom surface 10 and the second bottom surface 20 are both curved structures, thereby improving the pressure bearing capacity of the fuel chamber. Since the pressure bearing capacity of a curved surface is higher than that of a flat surface of the same thickness, the curved surface can evenly disperse the pressure along the entire surface and evenly diffuse the pressure to various parts of the bottom surface, so that the curved surface can withstand greater pressure, thereby improving the structural strength of the bipropellant injector.

[0070] Specifically, at least one side of the fuel chamber 50 is provided with a fuel inlet 51, and the fuel inlet 51 is used to introduce fuel into the fuel chamber 50. Preferably, the fuel inlet 51 is provided on the vertical wall connecting the first bottom surface 10 and the second bottom surface 20, so that the injection direction of the fuel inlet 51 to the fuel is perpendicular to or at a certain angle to the extension direction of the injection unit structure. The fuel chamber 50 is constructed as a hyperbolic concave lens structure, and the first bottom surface 10 and the curved middle part of the second bottom surface 20 are close to each other, so that the flow area of the fuel chamber 50 at the fuel inlet 51 is larger, and the flow velocity of the fuel here is lower, while the flow area at the center of the fuel chamber 50 is small, and the flow velocity of the fuel here is higher, so that the pressure distribution inside the fuel chamber 50 is more uniform. Preferably, the above pressure distribution has been verified by three-dimensional fluid simulation analysis.

[0071] In the two-component injector provided in this embodiment, the fuel chamber 50 is constructed as a hyperbolic concave lens structure, and the first bottom surface 10 is close to the curved middle part of the second bottom surface 20, so that the fuel flow rate in the edge area of the fuel chamber 50 is lower, and the fuel flow rate in the central area of the fuel chamber 50 is higher, thereby making the fuel chamber 50 have an isostatic pressure uniform flow characteristic, and the flow distribution of each injection unit structure is more uniform, which is beneficial to improving the injection combustion efficiency.

[0072] Specifically, Figure 5 As shown, at least one sweating cooling channel 11 is also provided through the first bottom surface 10 .

[0073] Specifically, the transpiration cooling channel 11 is configured as a meandering structure.

[0074] The transpiration cooling channel 11 penetrates through the first bottom surface 10 in a meandering channel arrangement form, enabling the fuel agent chamber 50 to communicate with the outside. In the application environment of the bi-component injector, the outside is usually the combustion chamber, that is, the fuel agent chamber 50 and the combustion chamber are separated by the first bottom surface 10, and the transpiration cooling channel 11 provided on the first bottom surface 10 conducts the fuel agent chamber 50 and the combustion chamber 80. Since the first bottom surface 10 is close to the side of the combustion chamber 80 and the temperature of the combustion chamber 80 is relatively high, the first bottom surface 10 needs to adopt cooling measures for cooling. Therefore, the first bottom surface 10 is usually processed with a special porous metal material, and the first bottom surface 10 is also usually referred to as a porous panel.

[0075] The bi-component injector provided in this embodiment arranges a group of transpiration cooling channel structures with a meandering structure on the first bottom surface 10, enabling the fuel agent in the fuel agent chamber 50 to slowly flow out from the meandering channel, thereby playing a role in transpiration cooling on the gas surface of the first bottom surface 10.

[0076] Specifically, the bi-component injector further includes:

[0077] An oxidant chamber 40, the oxidant chamber 40 has the second bottom surface 20 as the bottom and the third bottom surface 30 set away from the first bottom surface 10 as the top.

[0078] The bi-component injector is configured as a three-bottom two-chamber structure. The three bottoms are the first bottom surface 10, the second bottom surface 20, and the third bottom surface 30. A fuel agent chamber 50 is formed between the first bottom surface 10 and the second bottom surface 20, and an oxidant chamber 40 is formed between the second bottom surface 20 and the third bottom surface 30. At least one side of the oxidant chamber 40 is provided with an oxidant inlet 41, and the oxidant inlet 41 is used to introduce oxidant into the oxidant chamber 40. Preferably, the oxidant inlet 41 is provided on the vertical wall surface connecting the second bottom surface 20 and the third bottom surface 30. The second bottom surface 20 is a curved surface structure, which can improve the structural strength of the bi-component injector.

[0079] Specifically, a number of injection unit structures with different lengths are provided between the first bottom surface 10 and the second bottom surface 20.

[0080] Since a plurality of injection unit structures are provided in the fuel agent chamber 50, the distribution forms of the plurality of injection unit structures in the fuel agent chamber 50 can be honeycomb distribution, checkerboard distribution, concentric circle distribution, etc. In addition, the structural forms of the injection unit structures include self-impacting type, mutual-impacting type, coaxial direct current type, coaxial centrifugal type, etc. Preferably, in this embodiment, the injection unit structure adopts a coaxial direct current type injection unit structure.

[0081] This embodiment provides a bi-component injector. The injection unit structures arranged between the first bottom surface 10 and the second bottom surface 20 adopt different length designs, which can make the acoustic frequencies of the injection unit structures staggered, and is beneficial to improving the combustion stability.

[0082] Specifically, the injection unit structure is adapted to conduct the fuel agent chamber 50 and / or the oxidant chamber 40 to the outside; the injection unit structure includes:

[0083] A fuel agent nozzle 70, at least part of which is in communication with the fuel agent chamber 50, and one end of the fuel agent nozzle 70 is connected to the first bottom surface 10 and penetrates through the first bottom surface 10; and

[0084] An oxidant nozzle 60, its first end is connected to the second bottom surface 20 and penetrates through the second bottom surface 20 to communicate with the oxidant chamber 40, and its second end is at least partially arranged inside the fuel agent nozzle 70.

[0085] At least part of the fuel agent nozzle 70 is in communication with the fuel agent chamber 50. In this embodiment, specifically, it is communicated with the fuel agent chamber 50 through at least one radial hole 71 provided on the side wall of the fuel agent nozzle 70, and the radial hole 71 can facilitate the fuel agent to enter the injection unit structure.

[0086] One end of the fuel agent nozzle 70 is connected to the first bottom surface 10 and penetrates through the first bottom surface 10, so that a jet port 74 penetrating through the first bottom surface 10 is formed at the contact position between the injection unit structure and the first bottom surface 10.

[0087] The first end of the oxidant nozzle 60 is connected to and penetrates through the second bottom surface 20, so that an oxidant nozzle inlet end 61 penetrating through the second bottom surface 20 is formed at the contact position between the injection unit structure and the second bottom surface 20. The oxidant nozzle inlet end 61 communicates the oxidant chamber 40 with the injection unit structure, so that the oxidant located in the oxidant chamber 40 can enter the injection unit structure from the oxidant nozzle inlet end 61.

[0088] The second end of the oxidant nozzle 60 is at least partially arranged inside the fuel nozzle 70, and the fuel nozzle 70 and the oxidant nozzle 60 of the injection unit structure are arranged in a nested structure, and the oxidant nozzle 60 is arranged inside the fuel nozzle 70 to form a certain annular gap 73; at the same time, since the upper and lower parts of the injection unit structure are respectively connected to and penetrate the second bottom surface 20 and the first bottom surface 10, the oxidant nozzle 60 is penetrated inside, so that the oxidant nozzle 60 forms an oxidant nozzle outlet end 63 inside the fuel nozzle 70, and the oxidant nozzle 60 and the fuel nozzle 70 share the injection port 74, so that the fuel entering the injection unit structure through the radial hole 71 can be mixed with the oxidant entering from the oxidant nozzle inlet end 61 and flowing out from the oxidant nozzle outlet end 63, and the mixed fuel and oxidant are discharged from the injection port 74 together and injected into the combustion chamber 80.

[0089] Embodiment 3

[0090] Combination Figure 4 As shown, this embodiment provides a two-component injector which is different from the two-component injector provided in the second embodiment. In this embodiment, the first bottom surface 10 and the second bottom surface 20 are both planar structures, and at least one injection unit structure connected between the first bottom surface 10 and the second bottom surface 20 are injection unit structures of equal length.

[0091] Embodiment 4

[0092] The two-component injector described in the above-mentioned Embodiment 1, Embodiment 2 and Embodiment 3 is manufactured by 3D printing.

[0093] The bicomponent injector is made by 3D printing, which can reduce the development cost of the bicomponent injector and improve the production efficiency of the product. Relying on 3D printing technology, the three-bottom two-cavity injector structure and hundreds of injection units are printed together as an integral part, which greatly reduces the number of parts and reduces the product cost of the bicomponent injector. At the same time, the number of parts of the bicomponent injector is integrated from hundreds of pieces into one piece, which improves the production efficiency of the product, greatly shortens the production cycle, and helps to improve the inherent reliability of the product and improve the yield rate of the product. In addition, the integrated structural design reduces many manual links such as brazing and argon arc welding, creating conditions for the automated batch production of bicomponent injector products.

[0094] The curved and looped transpiration cooling channel structure groups are arrayed on the first bottom surface 10 by using the 3D printing process. The fuel slowly flows out from the curved channels, playing a role in transpiration cooling the gas surface of the first bottom surface 10. It has the same functions and effects as the traditional porous panel, but the cost is greatly reduced compared with the traditional porous panel, only 1 / 5 of the traditional porous panel. At the same time, due to the complex process and many procedures of the traditional porous panel, the first bottom surface 10 made by the 3D printing process has a simple process, few procedures, and the production cycle can be significantly shortened.

[0095] Preferably, the overall structure of the dual-component injector and the injection unit are manufactured by using the SLM laser printing forming process together.

[0096] Preferably, the powder material grade for 3D printing is GH3625, the powder particle size is 10 - 80 μm, it should be able to pass through the No. 100# sieve, and the weight of the powder particles passing through the No. 100# sieve is not less than 95%.

[0097] The main process flow of product production is: printing with an SLM laser 3D printing device → cleaning the product → hot isostatic pressing → solution heat treatment → machining → liquid flow test. The specific process method parameters are as follows:

[0098] Hot isostatic pressing: temperature range 1050 - 1180 °C, pressure greater than 150 MPa, holding and pressurizing time 3 - 5 h, argon protection, air cooling.

[0099] Solution heat treatment: temperature range 1090 °C - 1200 °C, holding for 2 h, rapid cooling with argon.

[0100] According to the use requirements, conduct the water flow resistance test on the oxidizer nozzle and the fuel nozzle. After the test is qualified, complete the product production.

[0101] Example Five

[0102] In this example, combined with specific examples, the dual-component injector provided in the above example is described in more detail. Preferably, the first bottom surface 10 and the second bottom surface 20 are both curved surface structures, making the fuel agent cavity 50 constructed as a hyperbolic concave lens structure, and the spherical arc radius of the first bottom surface 10 and the second bottom surface 20 is preferably selected to be 2 - 4 times the diameter of the dual-component injector.

[0103] Preferably, the radial holes 71 are raindrop-shaped. Each fuel agent nozzle 70 is provided with 2 rows of radial holes, 4 in each row, and the radial holes 71 are circumferentially evenly distributed on the side wall of the fuel agent nozzle 70. The total area of the raindrop-shaped radial holes is preferably 4 - 6 times the area of the annular gap 73.

[0104] Preferably, the oxidizer nozzle 60 is coaxially arranged with the fuel nozzle 70, and its axis is parallel to the axis of the bi-component injector. The outlet end 63 of the oxidizer nozzle is indented 4-10 mm relative to the injection port 74.

[0105] Upstream of the oxidizer nozzle 60, two Laval-type throttle holes are adopted, as Figure 3 shown. The diameter D1 of the throttle hole is calculated according to the following formula 1.

[0106] Formula 1:

[0107] Where, Qo - the oxidizer flow rate of each injection unit

[0108] Cdo - the flow coefficient of the oxidizer nozzle, generally 0.75-0.95

[0109] D1 - the diameter of the throttle hole

[0110] ρ - the density of the oxidizer

[0111] Pio - the pressure in the oxidizer chamber

[0112] Pe - the combustion chamber pressure

[0113] An annular cavity is provided upstream of the annular gap formed by the fuel nozzle and the oxidizer nozzle. The cross-sectional area of the annular cavity is generally 3-5 times that of the downstream annular gap, as Figure 3 shown. The dimensions D2 and D3 of the downstream annular gap are calculated according to the following formula 2.

[0114] Formula 2:

[0115] Where, Qf - the fuel flow rate of each injection unit;

[0116] Cdf - the flow coefficient of the fuel nozzle, generally 0.7-0.9

[0117] D2 - the outer diameter of the annular gap

[0118] D3 - the inner diameter of the annular gap

[0119] ρ - the density of the fuel

[0120] k - the fuel adiabatic index

[0121] Pif - the pressure in the fuel chamber

[0122] Pe - the combustion chamber pressure

[0123] The structure of the zigzag transpiration cooling channel in the first bottom surface 10 is as Figure 5As shown, the channel diameter D4 is preferably selected to be 0.1 - 1.0 mm, the amount of transpiration coolant accounts for 1% - 10% of the total amount of fuel agent, each channel is evenly distributed on the first bottom surface 10, and the distance between each channel is not greater than 10 mm.

[0124] Obviously, the above embodiments are merely examples for clear illustration and not limitations on the implementation manners. For those of ordinary skill in the art, other different forms of changes or variations can be made based on the above description. It is not necessary and impossible to enumerate all implementation manners here. And the obvious changes or variations derived therefrom are still within the protection scope of the present invention.

Claims

1. A two-component injector, characterized in that, Comprising: A fuel agent nozzle (70) having at least one radial hole (71) provided on its side wall; An oxidizer nozzle (60) at least partially sleeved inside the fuel agent nozzle (70); The inside of the oxidizer nozzle (60) is penetrated and is in communication with the radial hole (71) and the injection port (74) together; A fuel agent chamber (50); A first bottom surface (10) provided at the bottom of the fuel agent chamber (50); A second bottom surface (20) provided at the top of the fuel agent chamber (50) and oppositely arranged with the first bottom surface (10); And At least one injection unit structure as described above, the injection unit structure being communicatively arranged between the first bottom surface (10) and the second bottom surface (20); Both the first bottom surface (10) and the second bottom surface (20) are curved surface structures, and the middle parts of the curves are close to each other, so that the fuel agent chamber (50) is constructed into a hyperbolic concave lens type structure.

2. The dual-component injector according to claim 1, wherein At least one throttle hole (62) is provided on the inner side wall of the end of the oxidizer nozzle (60) away from the injection port (74).

3. The dual-component injector according to claim 2, wherein, Two throttle holes (62) are continuously provided on the inner side wall of the end of the oxidizer nozzle (60) away from the injection port (74).

4. The dual-component injector according to claim 1, characterized in that, The radial hole (71) is in a raindrop shape structure.

5. The dual-component injector according to any one of claims 1-4, characterized in that, An annular cavity (72) is formed between the inner side wall of the fuel agent nozzle (70) and the outer side wall of the oxidizer nozzle (60).

6. The dual-component injector according to claim 5, wherein The radial hole (71) is arranged facing the annular cavity (72).

7. The dual-component injector according to claim 5, characterized in that, An annular gap (73) is further formed between the inner side wall of the fuel agent nozzle (70) and the outer side wall of the oxidizer nozzle (60), one end of the annular gap (73) is in communication with the annular cavity (72), and the other end is in communication with the injection port (74).

8. The dual-component injector according to claim 1, characterized in that, A plurality of injection unit structures with different lengths are provided between the first bottom surface (10) and the second bottom surface (20).

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